STAR-C -CCM+ CM+ Applied ied to AIAA HiLif LiftW tWS1 S1 D. - PowerPoint PPT Presentation

High gh-Lif Lift t Aerodyn dynamics amics: : STAR-C -CCM+ CM+ Applied ied to AIAA HiLif LiftW tWS1 S1 D. Snyder er

Aer erospa space ce App pplic icati tion on Area eas Aerodyna nami mics cs – Subsonic through Hypersonic – Aeroacoustics – Store release & weapons bay analysis – High lift devices – Stage separation – Plume analysis – Ablation – Engine integration

Aer erospa space ce App pplic icati tion on Area eas Aerodyna nami mics cs – Subsonic through Hypersonic – Aeroacoustics – Store release & weapons bay analysis – High lift devices – Stage separation – Plume analysis – Ablation – Engine integration Propulsi sion on Systems ems – Pumps – Rocket Motor, Ramjet, & Scramjet – Fans and Turbines – Combustion, sprays, chemistry – Inlets & ducting – Nozzles – Fuel systems, sloshing – Filters

Aer erospa space ce App pplic icati tion on Area eas Aerodyna nami mics cs Heat Transfer er and Thermal al – Subsonic through Hypersonic Manageme agement nt – Aeroacoustics – Mechanical Systems – Store release & weapons bay analysis (APU’s, undercowling, etc.) – High lift devices – Ice Protection – Stage separation – Avionics / Electronics Systems – Plume analysis – Battery Heat Management – Ablation – Heat Exchangers – Engine integration – Blade cooling – Other Conjugate Heat Transfer Propulsi sion on Systems ems – Pumps – Rocket Motor, Ramjet & Scramjet – Fans and Turbines – Combustion, sprays, chemistry – Inlets & ducting – Nozzles – Fuel systems, sloshing – Filters

High gh-Lif Lift t Aerodyn dynamics amics Aerod odynamics ynamics of 3D swep ept t wings gs in high-lif ift t conf nfigu gurat ations ions is very y compl plex – Separation – Unsteadiness – Confluent boundary layers – Transition – Vortical flow AIAA AI AA HiLif iftW tWS1 S1 (2010) 0) – Assess capabilities of current-generation codes • Meshing • Numerics • Turbulence Modeling • High-performance computing

NASA ‘Trap Wing’ Model Tested ed in 1998 98-1999, 99, 2002 02-2003 2003 at NAS ASA Lang ngle ley y and NAS ASA Am Ames es wind nd tun unne nels Re ~ 4.6M 6M – No turbulent trips – transition is a factor Data collect lected ed – Aerodynamic forces/moments * – Pressure distributions * – Transition location – Acoustics Trap Wing in NASA LaRC 14x22 WT * Evaluated in HiLiftWS1

Computation putational al Domain ain Geome ometr try y provided vided in IGES ES forma rmat – Minor surface cleanup “Configuration 1” – Slats at 30 deg, Flaps at 25 deg – Fully-deployed configuration Farfiel ield boundar ndaries ies created d in STAR AR-CCM CM+ – Extend 100MAC in all directions

Boundar dary y Condit ditions ions No-slip No lip wall conditions nditions – No transition location specified Symm mmetr try y plane ne Frees eestr tream eam – Mach 0.2 – T = 520R – P = 1 ATM – (Re = 4.3M based on MAC) – a = 6, 13, 21, 28, 32, 34, 35, 36, 37 deg

Mesh Overvie iew Polyhe yhedral dral mesh sh – Wide range of angles of attack on a single mesh – Strong streamline curvature – Massive recirculation regions Prism m layer ers – 30 layers Grid refinem inement nt study udy – Results from Medium grid are presented Grid Size Number of cells Very Coarse 10M Coarse 21M Medium 34M Fine 43M * Very Coarse mesh shown (10M cells)

Addit ition ional al Mesh h Features tures Text * Very Coarse mesh shown (10M cells)

Solver er Sett ettings gs Densi nsity ty-Ba Base sed d Coupled upled Solver er – Low Mach number preconditioning 2nd-order der sp spatial al disc scre retizati tization on Stea eady dy-st stat ate e RAN ANS S equa uation ions ) k- w Tur SST T (Ment nter) urbulence ulence Mode del – Integrated to the wall – 1st prism layer y+ < 1.0 – g -Re θ Transition Model

Transit ansition ion Model AoA=13° Transition g -Re Re θ Trans nsiti ition on Model – Predicts laminar-turbulent transition in the boundary layer – Correlation-based model formulated for unstructured CFD codes – Models transport of Momentum Thickness Re and Intermittency Without out tran ansiti ition on modeling ing – Lift coefficient generally underpredicted – Stall predicted too late

Converge ergence ce Behavior ior 3.5 Turn on transition model 3 2.5 2 CL 6 degrees 1.5 13 degrees 21 degrees 1 28 degrees 32 degrees 0.5 34 degrees 0 0 2000 4000 6000 8000 10000 12000 14000 Iterations (n) * At higher angles of attack, stability required running without transition model for a time.

Comple plex x Flowfield ield AOA=6 =6 AOA=13 AOA=2 =28 AOA=3 =37

Lift t Pred edicti iction on Configuration 1 3.5 Experiment 3 STAR-CCM+: Medium 2.5 2 CL 1.5 1 0.5 0 -5 0 5 10 15 20 25 30 35 40 Angle of Attack (Degrees)

Lift t Pred edicti iction on Configuration 1 3.5 Experiment 3 STAR-CCM+: Medium 2.5 2 CL 1.5 1 0.5 0 -5 0 5 10 15 20 25 30 35 40 Angle of Attack (Degrees)

Drag g Predic edictio tion 1 Experiment 0.9 STAR-CCM+: Medium 0.8 0.7 0.6 CD 0.5 0.4 0.3 0.2 0.1 0 -5 0 5 10 15 20 25 30 35 40 Angle of Attack (Degrees)

Pitch tching ing Momen ent t Predic edicti tion on 0 Experiment STAR-CCM+: Medium -0.1 -0.2 CM -0.3 -0.4 -0.5 -0.6 -5 0 5 10 15 20 25 30 35 40 Angle of Attack (Degrees)

Pressure essure Data Pressur ssure e mea easure sureme ments nts were ere made de at ~800 00 locati tions ons on the e wing g sur urface face Similar ilarly ly, CFD data was s extr tract cted ed at 9 corres rrespond ponding ng sp spanwis wise locati tions ons 0.17 0.28 0.41 0.50 0.65 0.70 0.85 CFD data extraction Experimental pressure tap locations 0.95 0.98 locations

Cp Cp Comparison: η=0.50 (mid -span) an) AoA=6° AoA=21° AoA=34° AoA=37°

Cp Cp Comparison arison : η=0.95 (tip) AoA=6° AoA=21° AoA=34° AoA=37°

Conclusions lusions STAR AR-CC CCM+ M+ accur urat ately ely predict dicted ed the e aerodynamic behavior of the NASA ‘Trap AoA=6° Wing’ high -lif lift t case se – Lift, drag, and pitching moment – Pressure distribution Proper per mesh shing ing techni chniques es were re imp mpor orta tant nt – Boundary layer – Element wake interactions AoA=21° – Massive separation region – Tip vortex Trans nsit ition ion mode deling ing was necess cessar ary – Fully-turbulent under-predicted lift at high AoA (pre-stall) – Fully-turbulent over-predicted stall AoA

Upcomi Up ming HiLif iftW tWS1 S1 Speci cial al Sessi sion on (Jun une e 2012) 12) – Addition of support brackets – Hysteresis effects Aeroe oelas astic tic Predic dicti tion on Worksh kshop op (Ap April l 2012) 12) Propulsi ulsion on Aerodyn odynamic amics s Worksh kshop op (Jul uly y 2012) 12) Eglin Store Eg re Separa rati tion on Valida dati tion on

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